The National Aero-Space Plane (NASP) is unique in its integration of the airframe and propulsion system. The performance of the NASP propulsion system (scramjet) is dependent upon the quality of the flow into the scramjet inlet. Hence, the calculation of the inlet flow field must be coupled to the forebody flow field for accurate performance predictions. The Compressible Navier-Stokes code has been extended to perform both external and internal hypersonic flow fields. Computations are presented that validate these changes and demonstrate the capability to perform coupled forebody/inlet computations for hypersonic flows.


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    Title :

    Calculation of hypersonic forebody/inlet flow fields


    Contributors:

    Publication date :

    1990-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


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